• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an actuator (4) for controlling a horizontal stabilization plane (3) of an aircraft, comprising: - a primary track comprising a screw (6) and a primary nut (7), the primary nut (7) being adapted to cooperate with the screw (6), so that a rotation of the screw (6) relative to the primary nut (7) along an axis of rotation (X) causes a translation of the primary nut (7) with respect to the screw (6) along the axis (X), for moving the horizontal stabilizing plane (3), - a secondary channel comprising a secondary part (25, 28), and a housing ( 23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with a clearance between the secondary part and the housing, in which the secondary channel further comprises a clearance device (27). ), configured to, in case of breakage of the primary path causing displacement of the secondary part (25, 28) with respect to the housing, cancel the clearance between the secondary part (25, 28) and the housing (23, 26) to maintain the secondary part (25, 28) in contact with the housing (23, 26).
    公开号:FR3016607A1
    申请号:FR1450421
    申请日:2014-01-20
    公开日:2015-07-24
    发明作者:Bruno Antunes；Christian Gouard；Herve Gorecki；Jerome Mehez；Jesus-Angel Humanes
    申请人:Sagem Defense Securite SA；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to an actuator for controlling a horizontal plane stabilizing an aircraft, and a stabilization assembly 5 comprising such an actuator. STATE OF THE ART In aircraft, the horizontal stabilization plane, located at the rear of the aircraft, serves to provide trim compensation (trim) of the aircraft in flight phase. The horizontal plane is pivotally mounted relative to the fuselage of the aircraft and is mechanically actuated by a Horizontal Stabilizer Trim Actuator (HSTA). The actuator generally comprises a screw connected to the fuselage of the aircraft and a nut connected to the horizontal plane. The screw is rotated by a motor control unit (MCU) according to the commands generated by the driver. The rotation of the screw results in a translation of the nut along the screw, which has the effect of rotating the horizontal plane relative to the fuselage. The loss of mechanical connection between the structure of the aircraft and the horizontal plane is a catastrophic event. Therefore, horizontal plane actuators generally include two mechanical paths: a "main track" (or "primary track") and a "secondary track" to take over the primary track in case of breakage of the track. primary pathway. However, in most known actuators, the two channels comprise common parts which are stressed both during operation of the primary channel and during operation of the secondary channel. These include the connecting pieces connecting the actuator to the fuselage of the aircraft and the horizontal stabilization plane. In case of breakage of a common part, the two ways become unavailable.
    [0002] Moreover, it is generally not possible to detect the commitment of the secondary path, so that the pilot is not informed of the failure.
    [0003] SUMMARY OF THE INVENTION An object of the invention is to provide a control actuator of a horizontal stabilization plane for limiting the stresses applied to the parts of the secondary channel. This problem is solved in the context of the present invention by means of a control actuator of a horizontal stabilization plane of an aircraft, comprising: a primary track comprising a screw and a primary nut, the primary nut being clean to cooperate with the screw, so that a rotation of the screw relative to the primary nut along an axis of rotation causes a translation of the primary nut relative to the screw along the axis, to move the plane stabilizing horizontal, - a secondary channel comprising a secondary part and a housing, the secondary part being mounted in the housing with a clearance between the secondary part and the housing, 20 in which the secondary channel further comprises a play catch-up device , the play-catching device comprising a play-catching piece having a clamping ramp inclined with respect to the axis, the play-catching device being arranged to, in case of breakage, re of the primary path causing a displacement of the secondary part relative to the housing along the axis in a first direction tending to reduce the clearance between the secondary part and the housing, move the play compensating piece to a blocking position in which the play-compensating piece prevents movement of the secondary part relative to the housing in a second direction, opposite to the first direction, the play-catching part coming to clamp the secondary part against the housing via the clamping ramp so as to keep the secondary part in contact with the housing.
    [0004] In such an actuator, the clearance provided between the secondary part and the housing makes it possible to preserve the secondary part from any stress as long as the secondary channel is not engaged. In the event of a break in the primary path, the slack adjuster makes it possible to bring the secondary part into contact with the housing by eliminating the clearance, which makes it possible to drive the horizontal stabilization plane via the secondary path. In addition, the clamping ramp ensures complete clearance of the clearance between the secondary part and the housing, including play due to machining tolerances of the parts and deformations of the actuator parts under the aerodynamic forces, which avoids a float of the horizontal plane of stabilization. The actuator may furthermore have the following features: the play-catching piece is rotatably mounted relative to the casing between an armed position allowing clearance between the secondary part and the casing and the blocking position; play catch is rotatably mounted about an axis of rotation parallel to the axis of rotation of the screw, - the clamping ramp is a helical ramp, - the play catch device comprises a return elastic member 20 arranged for urging the play compensating piece towards the locking position, - the elastic return element comprises a torsion spring, - the play catching device comprises a second play catching piece mounted movably in translation relative to the housing, between a first position in which the second play-catching piece engages with the first play-catching piece to hold the first piece catching up game in an armed position, and a second position in which the second play-catching piece is released from the first play-catching piece to allow movement of the first game-catching piece to the blocking position. the first play-catching piece comprises teeth and the second play-catching piece comprises teeth that are adapted to engage the teeth of the first play-catching piece when the second play-catching piece is in the first play-catching piece. position, so as to prevent a displacement of the first play catching piece to the locking position, - the second clearance play piece comprises a ramp adapted to cooperate with the ramp of the first play catch-up piece for tightening the play. secondary part against the housing, - the secondary part is a rod extending inside the screw, - the primary channel comprises a joint primary cardan shaft for connecting the screw to the fuselage of the aircraft, and the secondary track comprises a secondary universal joint for connecting the casing to the fuselage, the primary universal joint and the secondary universal joint having rotational axes combined, the secondary part is a secondary nut adapted to cooperate with the screw, so that a rotation of the screw relative to the secondary nut along the axis of rotation of the screw causes a translation of the secondary nut relative to to the screw along the axis, - the primary track comprises a primary universal joint for connecting the primary nut to the horizontal stabilization plane, and the secondary track 20 comprises a secondary universal joint to connect the housing to the horizontal stabilization plane , the primary universal joint and the secondary universal joint having axes of rotation combined, - the housing comprises a window allowing the insertion of a tool inside the casing for rowing The first play compensating piece in the armed position, the actuator comprises one or more position sensor (s) for detecting the position of the first play catch-up piece, the first play-catching piece comprises a or several magnet (s) and the position sensor (s) are Hall effect sensors 30 for detecting the presence of the magnet (s) when the magnet (s) is (are) positioned (s) facing the sensor (s). The invention also relates to a horizontal stabilization assembly of an aircraft, comprising: - a horizontal stabilization plane of the aircraft, and - a control actuator as defined above for moving the horizontal plane of stabilization.
    [0005] PRESENTATION OF THE DRAWINGS Other characteristics and advantages will become apparent from the description which follows, which is purely illustrative and not limiting and should be read with reference to the appended figures, among which: FIG. 1 is a general view of an aircraft comprising a horizontal plane of stabilization; - Figure 2 schematically shows a horizontal stabilization assembly comprising a horizontal stabilization plane and an associated actuator; - Figures 3 to 6 schematically represent a control actuator of a horizontal plane of stabilization according to an embodiment of the invention, - Figure 7 is a detail view, in section AA, of a first play catch device, - Figure 8 is a detailed view, in AA section, of a second clearance device, - Figure 9 shows schematically the control actuator of a horizontal stabilization plane, FIG. 10 is a diagrammatic representation of various constituent parts of the first play-catching device, FIG. 11 schematically shows different components of the second play-catching device, FIGS. 12 to 14 diagrammatically show three FIGS. FIG. 1 shows the aircraft 1 represented as an aircraft comprising a horizontal stabilization plane (or stabilizer) 3 mounted to be movable relative to the fuselage 8. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT of the plane to control the plane in pitch.
    [0006] As illustrated in FIG. 2, the position of the horizontal stabilization plane 3 is regulated by an actuator 4 making it possible to pivot the horizontal stabilization plane 3 with respect to the fuselage 8. The horizontal stabilization plane 3 is rotatably mounted relative to the fuselage 8 of the aircraft about an axis Z. The actuator 4 comprises a motorized control unit 5, a screw 6 and a nut 7. The motorized control unit 5 comprises an electric motor and a mechanical assembly of reduction (not shown in this figure). The motorized control unit 5 is connected to the fuselage 8 of the aircraft with a universal joint 9. The motorized control unit 5 is adapted to rotate the screw 6 relative to the fuselage 8 about an axis of rotation. X. Furthermore, the nut 7 is immobilized in rotation, while being movable in translation relative to the fuselage 8. The screw 6 has a first end 10 connected to the motorized control unit 5 and a second end 11, opposed to the first end 10. The nut 7 is adapted to cooperate with the screw 6 by means of helical grooves, so that a rotation of the screw 6 relative to the nut 7 causes a translation of the nut 7 relative to the screw 6 in a direction 20 parallel to the axis X of rotation of the screw 6. The horizontal plane 3 is connected to the nut 7 via a universal joint 12. To adjust the position of the horizontal plane of stabilization 3 compared to the fuselage 8, the pilot controls the power supply of the motorized control unit 5. The motorized control unit 5 rotates the screw 6 relative to the fuselage 8, which has the effect of moving the nut 7 in translation relative to the fuselage 8 along the the screw 6. The displacement of the nut 7 in translation, causes a rotation of the horizontal plane of stabilization 3 relative to the fuselage 8 of the aircraft around the axis Z. According to the direction in which the screw 6 is driven in rotation, the stabilizing horizontal plane 3 is moved in a first direction (arrow A) or in a second direction (arrow B), opposite to the first direction. The actuator 4 is shown in more detail in FIGS. 3 to 9.
    [0007] In these figures, the actuator 4 comprises a primary track and a secondary track, each track connecting the horizontal stabilization plane 3 to the fuselage 8 of the aircraft. The primary track comprises a first primary connection assembly 5 9, a motorized drive unit 5, a screw 6, a primary nut 7 and a second primary connection assembly 13. The motorized control unit 5 comprises a housing 14, an electric motor 15 and a mechanical reduction assembly 16 for driving the screw 6 in rotation about an axis of rotation X. The first primary connection assembly 9 comprises a cardan joint by which the housing 14 of the unit motorized training is connected to the fuselage 8 of the aircraft. The screw 6 is rotatably mounted relative to the housing 14 about the axis X. The screw 6 has a first end 10 (or receiving end) 15 for receiving a driving torque, and a second end 11 (or end free), opposite to the first end 10. The first end 10 of the screw 6 extends inside the housing 14 of the motorized control unit 5, and is connected to the motor 15 via the mechanical assembly of reduction 16. The screw 6 comprises a body 17 having a cylindrical outer surface in which is formed a helical groove 18. Moreover, the screw 6 has a longitudinal bore 19 extending inside the body 17 of the screw 6. The primary nut 7 extends around the body 17 of the screw 6. The primary nut 7 has a cylindrical internal surface in which is also provided a helical groove 20. The screw 6 and the primary nut 7 cooperate e between them through the helical grooves 18 and 20 in which are housed balls 21, so that a rotation of the screw 6 relative to the primary nut 7 concomitantly causes a translation of the primary nut 7 relative to the screw 6 in the direction of the axis X. The second primary connection assembly 13 comprises a second universal joint by which the primary nut 7 is connected to the horizontal stabilization plane 3.
    [0008] The secondary path includes a first secondary link assembly 22, a first housing 23 (or rod housing), a first clearance adjuster 24, a rod 25, a second housing 26 (or nut housing), a second housing 23, backlash device 27, a secondary nut 28 and a second secondary link assembly 29. The first secondary linkage assembly 22 includes a universal joint by which the rod housing 23 is connected to the fuselage 8 of the aircraft. The first primary connection assembly 9 and the first secondary connection assembly 22 have axes of rotation Y1 and Y2 coincide.
    [0009] The rod 25 extends inside the screw 6, in the longitudinal bore 19 of the screw 6. The rod 25 has a first end 30 and a second end 31, opposite the first end 30. The first end 30 of the rod 25 is received in the rod housing 23 with an axial clearance J1 (clearance measured in the direction of the X axis) between the rod 25 and the rod housing 23. The second end 31 is attached to the second end 11 of the screw 6. In this way, the rod 25 is secured to the screw 6. More specifically, the rod 25 comprises at the first end 30 an end portion having a larger diameter. The enlarged diameter end portion extends inside the stem housing 23. Furthermore, the rod 25 is rotatably mounted relative to the rod housing 23 about the X axis. The first retrieval device of FIG. clearance 24 extends inside the stem casing 23. The first play-catching device 24 comprises a first play-catching piece 32, a second play-catching piece 33 and an elastic return member 34 (FIG. Figure 7). The first play-catching piece 32 is rotatably mounted relative to the nut housing 23 about the X axis, which is also the axis of rotation of the screw 6. The second play-catching piece 33 is mounted movable in translation along the axis X relative to the housing 30 of nut 23. The resilient return element 34 comprises a torsion spring arranged to urge the first play compensating piece 32 in rotation around the X axis .
    [0010] As illustrated in FIG. 11, the first play-catching piece 32 comprises teeth 35 adapted to engage teeth 36 of the second play-catching piece 33. More specifically, the first play-catching piece 32 comprises three teeth 35. The second play compensating piece 33 also comprises three teeth 36 adapted to be inserted between the three teeth 35 of the first play catch piece 32. In addition, the teeth 35 of the first play catch piece clearance 32 have guide surfaces 38 inclined relative to the direction 10 of the X axis, forming ramps. More specifically, the ramps 38 are helical ramps, having the axis X as the axis. Similarly, the teeth 36 of the second play compensating piece 33 have guide surfaces 39 inclined relative to the direction of the axis. X, forming ramps. The ramps 39 are also helical ramps, having the X axis as their axis. Furthermore, the rod housing 23 comprises a window 37 through which an operator can introduce a tool to move the first play catch piece 33 in rotation. around the X axis. The actuator 4 further comprises angular position sensors 50 to 53 for detecting the position of the first play compensating piece 32 relative to the housing 23. The sensors 50 to 53 detect the commitment of the secondary track and to transmit the information to the pilot. The sensors 50-53 are preferably non-contact sensors, such as Hall effect sensors, attached to the rod housing 23. The actuator 4 includes magnets attached to the first play pickup piece 32. The sensors Hall effect 50 to 53 are able to detect the presence of magnets when the magnets are positioned opposite the sensors. The second secondary connection assembly 29 comprises a universal joint 30 through which the nut housing 26 is connected to the horizontal stabilization plane 3. The second primary connection assembly 13 and the second secondary connection assembly 29 have rotation axes confused.
    [0011] The secondary nut 28 extends around the body 17 of the screw 6. The secondary nut 28 has a cylindrical inner surface in which is formed a helical groove 38. The secondary nut 28 cooperates with the screw 6 by means of helical grooves 21 and 38 so that a rotation of the screw 6 relative to the secondary nut 28 about the X axis causes a translation of the secondary nut relative to the screw 6 along the X axis. this way, the rotation of the screw 6 concomitantly causes an identical translation of the primary nut and the secondary nut 28 relative to the screw 6 in the direction X.
    [0012] The secondary nut 28 extends inside the nut housing 26, with an axial clearance J2 (clearance measured in the direction of the X axis) between the nut housing 26 and the secondary nut 28. The second slack adjuster 27 extends inside the nut housing 26. The second slack adjuster 27 is similar to the first slack adjuster 24. The second slack adjuster 27 comprises a first play-catching piece 42, a second play-catching piece 43 and an elastic return member 44. The first play-catching piece 42 is rotatably mounted relative to the nut casing 26 around the casing X axis, which is also the axis of rotation of the screw 6. The second clearance play piece 43 is mounted movable in translation along the X axis relative to the nut housing 26. The elastic return member 44 comprises a torsion spring arranged to solicit the first In the embodiment illustrated in FIG. 10, the secondary nut 28 and the second clearance adjuster 43 are one and the same piece. As illustrated in FIG. 10, the first play-catching piece 42 comprises teeth 45 adapted to engage teeth 46 of the second play-catching piece 43. More specifically, the first play-catching piece 42 comprises three teeth 45. The second piece of play clearance 43 also includes three teeth 46 adapted to be interposed between the three teeth 45 of the first piece of play catching 42.
    [0013] In addition, the teeth 45 of the first clearance play piece 42 have guide surfaces 48 inclined relative to the direction of the X axis, forming ramps. More precisely, the ramps 48 are helical ramps, having the X axis as an axis.
    [0014] Similarly, the teeth 46 of the second clearance play piece 43 have guide surfaces 49 inclined relative to the direction of the X axis, forming ramps. The ramps 49 are also helical ramps, having the X axis as their axis. Furthermore, the nut housing 26 comprises a window 47 through which an operator can introduce a tool to move the first play catch piece 43 into position. rotation around the axis X. The actuator 4 further comprises angular position sensors 60 to 63 for detecting the position of the first play-catching piece 42 with respect to the casing 26. The sensors 60 to 63 allow detect the commitment of the secondary path and transmit the information to the pilot. The sensors 60 to 63 are preferably non-contact sensors, such as Hall effect sensors, fixed on the nut housing 26. The actuator 4 comprises magnets fixed to the first play pick-up piece 42. The sensors Hall effect 60 to 63 20 are able to detect the presence of magnets when the magnets are positioned opposite the sensors. In normal operation, the motorized control unit 5 rotates the screw 6 about the X axis, which has the effect of moving the primary nut 7 in translation along the screw 6 along the X axis. The displacement of the primary nut 7 in translation causes a rotation of the horizontal plane of stabilization 3 relative to the fuselage 8 of the aircraft around the axis Z. The rod 25 being integral in rotation with the screw 6, the The rotation of the screw 6 concurrently causes a rotation of the rod 25 relative to the primary nut 7 and relative to the rod housing 23. In addition, the rotation of the screw 6 also has the effect of displacing the secondary nut. 28 in translation along the screw 6 along the X axis, the two nuts 7 and 28 move simultaneously in translation along the screw 6. Moreover, since the rod housing 23 is connected to the fuselage 8 via the connecting assembly 22 having axes of rotation Y1 and Y2 coinciding with the axes of rotation of the linkage assembly 9, the clearance J1 between the rod 25 and the rod housing 23 is kept constant. Likewise, since the nut housing 26 is connected to the horizontal stabilization plane 3 via the connection assembly 29 having axes of rotation Y3 and Y4 coinciding with the axes of rotation of the connection assembly 13, the housing nut 26 is also moved in translation relative to the screw 6, so that the clearance J2 between the secondary nut 28 and the nut housing 26 is kept constant. Due to the clearances J1 and J2 that exist between the rod 25 and the stem housing 23 on the one hand and between the nut 28 and the nut housing 26 on the other hand, the components of the secondary pathway do not transmit no effort between the fuselage 8 of the aircraft and the horizontal stabilization plane 3. The forces applying to the actuator 4 are only supported by the components of the primary track. In addition, during the normal operation of the actuator 4, the first play-catching piece 32 (respectively 42) of each play-catching device 24 (respectively 27) is in an armed position, and the second play-catching piece clearance 33 (respectively 43) is in the first position, as illustrated in FIG. 12. In this configuration, the second play-catching piece 33 (respectively 43) is engaged with the first play-catching piece 32 (respectively 42) to maintain the first play catching piece 32 (respectively 42) in the armed position. The teeth 36 of the second play-catching piece 33 (respectively 43) are interposed between the teeth 35 of the first play-catching piece 32 (respectively 42), so that the second play-catching piece 33 (resp. 43) prevents any rotational movement of the first play compensating piece 32 (respectively 42) relative to the housing 23 in a first direction (arrow C).
    [0015] In case of rupture of the first primary connection assembly 9 or the screw 6, the screw 6 is no longer connected to the fuselage 8 of the aircraft. The stabilizing horizontal plane 3, subjected to the action of air, then exerts a tensile force on the rod 25 of the secondary path. This has the consequence that the rod 25 is displaced in translation relative to the rod housing 23, the displacement of the rod 25 tending to reduce the clearance J1 between the rod 25 and the rod housing 23. The second piece of play catch-up 33 being integral in translation of the rod 23, the second clearance play piece 33 is displaced in translation relative to the rod housing 23 in the direction of the axis X in a first direction (arrow A). The second play-catching piece 33 is moved from the first position (FIG. 12) to the second position (FIG. 13) in which the second play-catching piece 33 is disengaged from the first play-catching piece 32. In other words, , the teeth 36 of the second play-catching piece 33 are no longer interposed between the teeth 35 of the first play-catching piece 32 and therefore no longer impede the rotation of the first play-catching piece 32. second play-catching piece 33 is in the second position, the second play-catching piece 33 allows a rotation of the first play-catching piece 34 with respect to the casing 23. Under the action of the elastic member of recall 34, the first piece of play catch 32 is rotated about the axis X in a first direction (arrow C). The first play-catching piece 32 passes from the armed position to a locking position (FIG. 14) in which the first play-catching piece 32 prevents a return of the second play-catching piece 33 to the first position (FIG. arrow B). In fact, the teeth 35 of the first play-catching piece 32 are opposite the teeth 36 of the second play-catching piece 33, so that the first play-catching piece 32 prevents any movement of the second play-off piece 32. play compensating piece 33 relative to the housing 23 in the direction of the axis X in a second direction (arrow B), opposite to the first direction. The teeth 36 come into axial abutment (in the direction of the X axis) against the teeth 35. In this way, the clearance J1 between the rod 25 and the stem housing 23 is canceled. In addition, the game J1 is automatically overtaken by the action 5 of the elastic return member 34. In addition, during the rotation of the first play-catching piece 32, the helical ramps 38 of the first piece of retracting clearance 32 slides on the helical ramps 39 of the second play compensating piece 33 so that the rotation of the first play catching piece 32 10 in the first direction (arrow C) has the effect of soliciting the second piece of play. backlash 33 parallel to the axis X in the first direction (arrow A), so that the rod 25 is pressed against the stem housing 23. In addition, the elastic return member 34 solicits the first piece of catching clearance 32 and prevents any rotation of the first game-catching piece in a second direction (arrow D), opposite to the first direction. In this configuration, the rod 25 is integral in translation with the rod housing 23 and transmits the forces applied to the actuator 4 between the horizontal stabilization plane 3 and the fuselage 8 via the first primary link assembly 9. Thus, the path secondary school takes over the primary path. During the maintenance of the actuator 4, it is possible to manually return the device to its initial configuration (FIG. 12), by introducing a tool through the window 37 formed in the stem casing 26 and rotating the first clearance piece 33 in the second direction (arrow D) against the force exerted by the elastic return member 34. The second play catching device 27 operates in the same manner as the first play catching 24.
    [0016] Similarly, in case of rupture of the second primary connection assembly 13 or the primary nut 7, the screw 6 is no longer connected to the fuselage of the aircraft 13. The horizontal stabilization plane 3, subjected to the action of the air, then exerts a traction force on the secondary nut 28 of the secondary path. This has the consequence that the secondary nut 28 is displaced in translation relative to the nut casing 26. The second play-catching piece 43 being integral in translation with the secondary nut 28, the second play-catching piece 5 43 is displaced in translation relative to the nut housing 26 in a first direction (arrow A), the displacement of the second play compensating piece 43 tending to reduce the clearance J2 between the nut 28 and the nut housing 26. The second play-catching piece 43 moves from the first position (FIG. 12) to the second position (FIG. 13) in which the second play-catching piece 43 is disengaged from the first play-catching piece 44. When the second play-catching piece 43 is in the second position, the second play-catching piece 43 allows a rotation of the first play-catching piece 42 with respect to the nut casing 26. Under the action of the elastic return member 44, the first play catch piece 42 is rotated in a first direction (arrow C). The first play-catching piece 42 moves from the armed position to a locking position (FIG. 14) in which the first play-catching piece 42 prevents a return of the second play-catching piece 43 to the second position (FIG. Arrow B). Indeed, the teeth 45 of the first play-catching piece 42 are opposite the teeth 46 of the second play-catching piece 43, so that the first play-catching piece 42 prevents any movement of the second play-back piece 43. clearance play piece 43 relative to the housing 26 in a second direction (arrow B), opposite to the first direction. In this way, the clearance J2 between the secondary nut 28 and the nut housing 26 is canceled. In addition, the game J2 is automatically overtaken by the action of the elastic return element 44.
    [0017] In addition, the helical ramps 48 and 49 of the clearance play pieces 42 and 43 cooperate with each other so that the rotation of the first play catch piece 42 in the first direction (arrow C) has the effect of displacing the second play retraction piece 43 in translation in the direction of the X axis in the first direction (arrow B), so as to tighten the secondary nut 28 against the nut housing 26. In this configuration, the nut secondary 28 is secured to the nut housing 26 and transmit the forces applied to the actuator 4 between the horizontal stabilization plane 3 and the fuselage 8 via the second primary connection assembly 29. Thus, the secondary path takes the relay on the primary pathway.
    权利要求:
    Claims (17)
    [0001]
    REVENDICATIONS1. Actuator (4) for controlling a horizontal stabilization plane (3) of an aircraft, comprising: - a primary track comprising a screw (6) and a primary nut (7), the primary nut (7) being clean to cooperate with the screw (6), so that a rotation of the screw (6) relative to the primary nut (7) along an axis of rotation (X) causes a translation of the primary nut (7) with respect to the screw (6) along the axis (X), for moving the horizontal stabilization plane (3), - a secondary path comprising a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with a clearance between the secondary part and the housing, in which the secondary channel further comprises a clearance device (27), the device for a backlash (27) comprising a play-catching piece (32, 42) having a clamping ramp (38, 48) inclined with respect to the axis (X), the play-catching device (2) 7) being arranged for, in case of breakage of the primary path causing displacement of the secondary part (25, 28) relative to the housing (23, 26) along the axis (X) in a first direction (A) tending to reduce the clearance between the secondary part and the housing, move the clearance play piece (32, 42) to a blocking position in which the clearance play piece (32, 42) prevents displacement of the secondary part ( 25, 28) relative to the housing (23, 27) in a second direction (B) opposite to the first direction, the play-catching piece (32, 42) clamping the secondary part against the housing via the clamping ramp (38,48) so as to maintain the secondary part (25,28) in contact with the housing (23,26).
    [0002]
    2. An actuator according to claim 1, wherein the clearance play piece (32, 42) is rotatably mounted relative to the housing (23, 26) between an armed position in which the clearance play piece (32, 42). allows clearance between the secondary part and the housing, and the blocking position.
    [0003]
    3. An actuator according to claim 2, wherein the clearance play piece (32, 42) is rotatably mounted about an axis of rotation parallel to the axis of rotation (X) of the screw (6).
    [0004]
    4. An actuator according to one of claims 2 and 3, wherein the clamping ramp (38, 48) is a helical ramp.
    [0005]
    5. An actuator according to one of claims 1 to 4, wherein the clearance device (32, 42) comprises an elastic return element (34, 44) arranged to urge the clearance play piece (32, 42) to the blocking position.
    [0006]
    The actuator of claim 5, wherein the biasing elastic member (34,44) comprises a torsion spring.
    [0007]
    7. An actuator according to one of claims 1 to 6, wherein the play catch device (27) comprises a second play catching piece (33, 43) mounted movable in translation relative to the housing (23, 26). ) between a first position in which the second play-catching piece (33,43) engages with the first play-catching piece (32,42) to hold the first play-catching piece (32,42). in a cocked position, and a second position in which the second play-catching piece (33, 43) is released from the first play-catching piece (32, 42) to allow movement of the first catch-up piece of play (32, 42) to the blocking position.
    [0008]
    An actuator according to claim 7, wherein the first play back piece (32, 42) comprises teeth (35, 45) and the second play back piece comprises teeth (36, 46) suitable for coming in engagement with the teeth (35, 45) of the first play compensating piece (32, 42) when the second play-catching piece (33, 43) is in the first position, so as to prevent movement of the first piece retracting clearance (32, 42) to the locking position.
    [0009]
    9. Actuator according to one of claims 7 to 8, wherein the second clearance play piece (33, 43) comprises a ramp (39, 49) adapted to cooperate with the ramp (38, 48) of the first piece. retraction device (32, 42) for clamping the secondary part (25, 28) against the housing (23, 27).
    [0010]
    10. Actuator according to one of claims 1 to 9, wherein the secondary part (25) is a rod extending inside the screw (6).
    [0011]
    An actuator according to claim 10, wherein the primary track comprises a primary universal joint (9) for connecting the screw (6) to the fuselage (8) of the aircraft, and the secondary track comprises a secondary universal joint ( 22) for connecting the housing (23) to the fuselage (8), the primary universal joint (9) and the secondary universal joint (22) having coinciding axes of rotation.
    [0012]
    12. Actuator according to one of claims 1 to 9, wherein the secondary part (28) is a secondary nut adapted to cooperate with the screw (6), so that a rotation of the screw (6) relative to the secondary nut (28) along an axis of rotation (X) causes a translation of the secondary nut (28) relative to the screw (6) along the axis (X).
    [0013]
    An actuator according to claim 12, wherein the primary track comprises a primary universal joint (13) for connecting the primary nut (7) to the horizontal stabilization plane (3), and the secondary track comprises a secondary universal joint (29) for connecting the housing (26) to the horizontal stabilization plane, the primary universal joint (13) and the secondary universal joint (29) having axes of rotation combined.
    [0014]
    14. Actuator according to one of claims 1 to 13, wherein the housing comprises a window (37, 47) allowing the insertion of a tool inside the housing (23, 26) to bring back the first piece of play catching (32, 42) in the armed position.
    [0015]
    15. An actuator according to one of claims 1 to 14, comprising one or more position sensor (s) (40-43, 50-53) for detecting the position of the first play compensating piece (32, 42).
    [0016]
    An actuator according to claim 15, wherein the first clearance compensating piece (32, 42) comprises one or more magnets and the position sensor (s) (40-43, 50-53) are Hall effect sensors for detecting the presence of the magnet (s) facing the sensor (s).
    [0017]
    17. A horizontal stabilization assembly of an aircraft, comprising: a horizontal stabilization rudder (3) for the aircraft, and a control actuator (4) according to one of claims 1 to 16 for moving the aircraft. horizontal plane of stabilization.
    类似技术:
    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    CN106458315B|2018-02-02|
    US20160340026A1|2016-11-24|
    WO2015107208A3|2015-09-11|
    US10040539B2|2018-08-07|
    FR3016607B1|2016-01-22|
    CN106458315A|2017-02-22|
    WO2015107208A2|2015-07-23|
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    法律状态:
    2015-01-21| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-22| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2017-01-13| CD| Change of name or company name|Owner name: SAGEM DEFENSE SECURITE, FR Effective date: 20161214 |
    2017-01-13| CJ| Change in legal form|Effective date: 20161214 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450421A|FR3016607B1|2014-01-20|2014-01-20|ACTUATOR FOR CONTROLLING A HORIZONTAL STABILIZATION PLAN OF AN AIRCRAFT|FR1450421A| FR3016607B1|2014-01-20|2014-01-20|ACTUATOR FOR CONTROLLING A HORIZONTAL STABILIZATION PLAN OF AN AIRCRAFT|
    US15/112,668| US10040539B2|2014-01-20|2015-01-20|Actuator for controlling a horizontal stabilizer of an aircraft|
    CN201580009903.9A| CN106458315B|2014-01-20|2015-01-20|For the actuator being controlled to the horizontal stabilizer of aircraft|
    PCT/EP2015/050945| WO2015107208A2|2014-01-20|2015-01-20|Actuator for controlling a horizontal stabiliser of an aircraft|
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